CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS) NO: BM-81 ISSUE: 2

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1 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP TYPE: PULSR (1) MANUFACTURER: P&M Aviation Ltd, Unit B, Crawford St, Rochdale, Lancs OL16 5NU (2) UK IMPORTER: N/A (3) CERTIFICATION: BCAR section S issue 6 (4) DEFINITION OF BASIC STANDARD: Airworthiness Submission PULSR, GA drawing YCT-000 issue A (5) COMPLIANCE WITH THE MICROLIGHT DEFINITION (a) MTOW (b) No. Seats 2 (c) Maximum Wing Loading (d) Vso (e) Permitted range of pilot weights Total Maximum crew weight (f) Typical Empty Weight (ZFW) (g) ZFW kg crew + 1 hr fuel (18litres /13 kg) (h) ZFW + 86 kg pilot + full fuel ( 78litres /56 kg) (i) Max ZFW at initial permit issue 450 kg (472.5kg with approved parachute fit) 36.3kg/m² (at 472.5kg) 39mph CAS kg front seat kg rear seat 220kg 250Kg 435Kg 392Kg 265Kg (287.5kg with approved parachute fit) TADS BM-81 issue 2 Page 1 of 12

2 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP (6) POWER PLANTS Designation Engine Type Reduction Gear Exhaust System Intake System Propeller Type Rotax 912 ULS 4 cylinder 4 stroke 2.43:1 gearbox CKT Single Muffler K&N intake filter Optional carb body heater Warp Drive Propeller Dia x Pitch o at tip Noise Type Cert No. 197M issue 1 Max Static RPM 4900 AAN approving configuration AAN BMAA-1067Issue 2 TADS BM-81 issue 2 Page 2 of 12

3 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP (7) MANDATORY LIMITATIONS: (A) Max Take-Off Weight (B) CG Limits (C) CG datum 450kg ( 472.5kg with approved parachute fit) N/A flexwing with predefined hang point on keel. Use rear position for PulsR trike. Nosewheel axle. (D) Cockpit Loadings (solo front seat only) Min Max Front 55kg 110kg Rear 0 110kg Total 55kg 220kg (E) Never Exceed Speed 120mph IAS (F) Manoeuvring Speed 90mph IAS (G) Permitted Manoeuvres (H) Fuel Contents (Max Useable) 45 Nose up / 45 nose down Non Aerobatic, max bank 60 o Normal acceleration limits, +4 / -0g 78L TADS BM-81 issue 2 Page 3 of 12

4 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP (I) Power Plant see Table Engine Max RPM MAX CHT MAX EGT Fuel Spec Engine Oil Spec Gearbox oil spec Fuel/Oil Mix Coolant Temperature ** Oil Pressure Oil Temperature Fuel Pressure Rotax 912 UL-S 5800max 5min contin. 135 o C 880 o C 87 MON or 95 RON minimum unleaded to EN 228 Super or UL91 or AVGAS 100LL.* Refer to Rotax Service Instruction SI Common supply with engine N/A 120 o C 2-5 bar above 3500 rpm o C bar *Unleaded preferred. See flight manual for limitations on AVGAS. ** A 50% Water/ethylene glycol mix required, coolant temperature must be monitored. (8) INSTRUMENTS REQUIRED: ASI Altimeter RPM CHT EGT (0-150mph.) 0-20,000 ft o C o C Coolant temp Oil Temp Oil Pres o C o C 0-8 bar TADS BM-81 issue 2 Page 4 of 12

5 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP (9) CONTROL DEFLECTIONS: N/A weight shift control limits defined by structure geometry. Control bar move right = roll left Control bar push out = pitch up Trim switch up = slow trim Push left pedal = taxi steering right Push left toe = brakes on Push right toe = throttle open Hand throttle forward = throttle open Ignition switches up = switch on Choke forward = choke on Tap aligned with body = fuel on (10) PILOT'S NOTES, MAINTENANCE MANUALS REFERENCES: 10.1 Manuals approved for use with this aircraft. (a) PulsR GTR Operator s manual issue 1 (b) Rotax 912S Operator s manual. (c) Rotax 912S Maintenance Manual The following placards are to be fitted:- (a) (b) (c) (d) Flight Limitations Placard (to be visible to pilot) See Annex D. Engine Limitations Placard (to be located near to engine instruments) N/A limitations are programmed into electronic instruments or marked as red lines on the instrument faces Fuel Limitations Placard (to be located near to filler cap) See Annex D. Switches See Annex D. TADS BM-81 issue 2 Page 5 of 12

6 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP (11) MANDATORY MODIFICATIONS / SERVICE BULLETINS / AIRWORTHINESS DIRECTIVES ETC: None. Annual Bettsometer test with a 1.2mm diameter needle, with wing sails fitted and tensioned to flight is to be carried out to: Upper & lower surface: 1000 grammes. Stitches: 1360 grammes using a minimum 1mm diameter hook, pull upwards. Technora reinforcement bands: 8kgf, sail to be slack for this test only. Note The GTR wing must be equipped with PulsR specific batten profiles. (12) MINIMUM ISA PERFORMANCE AT MAX TAKE-OFF WEIGHT Rate of Climb: Stall or Minimum Flying Speed: 1000fpm at 60mph IAS (912-S engine) 39mph IAS at MTOW / idle. TADS BM-81 issue 2 Page 6 of 12

7 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP Issue History Issue No. Reason and signatory 01 Initial Issue 02 To correct propeller pitch A C Love Illustration of Aircraft - 3 View TADS BM-81 issue 2 Page 7 of 12

8 Service Bulletins: CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP SB 132 & 133 Latest Edition. ANNEX A MANDATORY MODIFICATIONS/SERVICE BULLETINS CAA Mandatory modifications: Nil P&M compulsory modifications: Nil ANNEX B APPROVED OPTIONAL MODIFICATIONS Mod Ref PG-371 Description Instructor training bars The installation of all optional modifications is to be inspected by a BMAA inspector and an entry made in the appropriate logbook(s). Note that other approved modifications may exist which are not listed here. TADS BM-81 issue 2 Page 8 of 12

9 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP ANNEX C WEIGHING INFORMATION The table below is a guide only. Empty weights include unusable fuel, full oil, electrolyte and prepared ready for flight. ITEM WEIGHT kg PULS -912s Trike 190 GTR wing only 59 OPTIONAL ITEMS MAP BOX-FABRIC 0.76 LYNX ANTENNA 0.19 LYNX FILTER, POWER INT, PTT 0.81 INSTRUCTOR BARS 2.4 ICOM HAND HELD RADIO 0.3 TADS BM-81 issue 2 Page 9 of 12

10 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP ANNEXE D EXAMPLE PLACARDS Title Flight Limitations: Engine Limitations: Aircraft Weights: Baggage Limitations: Fuel Type, Capacity : Fuel Cock On/Off Positions: Ignition Switch On/Off Positions: Hand Throttle: Trimmer Setting: Tip Turn Adjusters: Latch Locking: Oil Type and Quantity: Fuel Load Limitations: Location On LH wing upright On panel On panel On baggage container Next To Filler Next to Tap On ignition switch bracket On throttle unit On trim switch (electric trim) On trim display (electric trim) On leading edge tube tips Next to latch On oil cap In the cockpit TRIM INDICATOR AND TRIM SWITCH PLACARDS TRIM FAST / DOWN SLOW / UP TADS BM-81 issue 2 Page 10 of 12

11 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP MAIN PLACARD P&M AVIATION PULSR FLIGHT LIMITATIONS MANOEUVRING SPD NEVER EXCEED Vne MAX CROSS WIND 90MPH 120MPH 12MPH ENGINE LIMITATIONS MAX OIL PRESSURE 7 BAR MIN OIL PRESSURE 1.5 BAR MAX OIL TEMP (912S) 130 DegC MIN OIL TEMP 50 DegC MAX CHT (912S) 135 DegC MAX COOLANT TEMP 120 DegC MAX CONT RPM 5500 MAX RPM 5800 PAYLOAD LIMITATIONS MAX. TAKE OFF WEIGHT WITH PARACHUTE MAX. COCKPIT LOAD MAX. P1 LOAD MAX PASSENGER LOAD MIN P1 LOAD 450KG 472.5KG 220KG 110KG 110KG 55KG DO NOT EXCEED MAX. LOAD WARNING DO NOT EXCEED 60 DEGREES ANGLE OF BANK DO NOT EXCEED 45 DEGREES IN PITCH THIS AIRCRAFT IS NON- AEROBATIC NO WHIPSTALLS, WINGOVERS, TAILSLIDES, LOOPS, ROLLS OR SPINS NO NEGATIVE G MAINTAIN POITIVE G LOADING AT ALL TIMES FLY SOLO FROM FRONT SEAT ONLY TADS BM-81 issue 2 Page 11 of 12

12 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP MISCELLANEOUS EXAMPLE PLACARDS. IGNITION SWITCH PLACARD IS SPLIT AND USED FOR BOTH MAG SWITCHES. (Note not all placards shown are fitted) TADS BM-81 issue 2 Page 12 of 12

13 Civil Aviation Authority EMERGENCY MANDATORY PERMIT DIRECTIVE Number: E Issue date: 21 November 2012 In accordance with 22(1) of Air Navigation Order 2009 as amended the following action required by this Mandatory Permit Directive (MPD) is mandatory for applicable aircraft registered in the United Kingdom operating on a UK CAA Permit to Fly. Type Approval Holder s Name: P&M Aviation Type/Model Designation(s): Pegasus Quik, Quik GT 450, QuikR and Quik GTR Title: Manufacturer: Applicability: Reason: Sail Reinforcement Degradation Additional Test P&M Aviation Ltd. Pegasus Quik, Quik GT450, QuikR and Quik GTR with X-05 or Technora reinforcement bands. An incident in 2011 with a 4 year/1500 Hours flight time sail showed that the standard Bettsometer test used to predict sail strength degradation could not be used. This issue was addressed by the application of MPD No Revision 1. Effective Date: 21 November 2012 A subsequent incident in September 2012, with a 6 year/1000 Hours flight time sail, has necessitated a revision to the previously defined test limits and compliance periods. Additionally, the applicability has been revised to incorporate the Quik GTR, which was not in production at the time of the original MPD. As such, P&M Aviation has revised Service Bulletin (SB) 132 to Issue 2 in order to reflect the revised criteria. This MPD supersedes MPD No R1. Mandatory Permit Directive E Page 1 of 2

14 Civil Aviation Authority Mandatory Permit Directive SRG Airworthiness Division Compliance/Action: For sails more than 2 years old or more than 500 hours flight time, whichever comes first, perform the tests as described in P&M Aviation Ltd Service Bulletin Number 132 Issue 2. This is to be achieved within the next 10 flight hours or 4 months from the effective date of this MPD, whichever occurs first. During this period high G manoeuvres must be avoided. For all aircraft, perform the tests as described in P&M Aviation Ltd Service Bulletin Number 132 Issue 2 at each annual inspection. In the event of the reinforcement bands failing the tests described in SB 132 Issue 2, the aircraft must not be flown until satisfactory resolution is received from P&M Aviation Limited. Note: a) A copy of Service Bulletin Number 132 Issue 2 may be obtained from: P & M Aviation Unit B Crawford Street Rochdale Lancashire OL16 5NU Tel: flying@pmaviation.co.uk Ensure compliance with this MPD is recorded in the aircraft logbook Reference Publications: P & M Aviation Ltd Service Bulletin Number 132 Issue 2 Remarks: 1. This MPD was not posted for consultation due to the urgency of the requirement. 2. Enquiries regarding this MPD should be referred to: Aircraft Evaluation and Surveillance Department, Civil Aviation Authority, Safety Regulation Group, Aviation House, Gatwick Airport South, West Sussex RH6 0YR. Tel: +44 (0) Fax: +44 (0) department.certification@caa.co.uk Mandatory Permit Directive E Page 2 of 2

15 Civil Aviation Authority MANDATORY PERMIT DIRECTIVE Number: Issue date: 22 November 2016 In accordance with Article 41(1) of The Air Navigation Order 2016, as amended, the following action required by this Mandatory Permit Directive (MPD) is mandatory for applicable aircraft registered in the United Kingdom operating on a UK CAA Permit to Fly. Type Approval Holder s Name: P&M Aviation Ltd Title: Type/Model Designation(s): Quik GTR, QuikR Wing Hang Bolt Installation Inspection and Modification Manufacturer: Applicability: Reason: P&M Aviation Ltd Quik GTR, QuikR Some instances of the hang bolt head rotating have been found with damage to the safety lanyard. The pinch nut slackens off, promoting fretting wear in the assembly. If left unchecked, eventually the lanyard could fail allowing the retaining nut to depart the aircraft and the main hang bolt to come out. The bolt rotation is driven by yawing loads between the trike and wing in turbulence. Effective Date: 25 November 2016 Note the hang bolt is intended to be tight and the bearing surface should be between the pylon top bearings and the pylon sleeve, not the hang bolt. Sometimes the nylon bearings swell and stick in the sleeve, new bearings are made in acetal which does not swell. Compliance/Action: Compliance is required as follows, unless previously accomplished: 1. Within the next 25 flying hours from the effective date of this MPD or at the next annual inspection, whichever is sooner, inspect the hang bolt for tightness and any evidence of rotation, as shown by twisting of the lanyard. See Figure 1 in P & M Aviation Ltd Service Bulletin 141. If there are signs of damage to any of the hang bolt components, obtain replacement components and carry out the action in paragraph 2 before further flight. 2. Within the next 25 flying hours from the effective date of this MPD or at the next annual inspection, whichever is sooner, install the hang bolt locking plate in accordance with paragraph 2 of P & M Aviation Ltd Service Bulletin 141. Mandatory Permit Directive Page 1 of 2

16 Civil Aviation Authority Mandatory Permit Directive SARG Compliance/Action Cont: 3. Record the inspection and any necessary rectification action from paragraph 1 and the modification action from paragraph 2 in the aircraft technical log in accordance with paragraph 3 of P & M Aviation Ltd Service Bulletin Inspect the security of the M6 bolt securing the locking plate every 50 flying hours in accordance with paragraph 3 of P & M Aviation Ltd Service Bulletin Inspect the hang bolt installation, including the locking plate and the tightness of the pinch nut, at each annual inspection in accordance with paragraph 4 of P & M Aviation Ltd Service Bulletin 141. ENSURE COMPLIANCE WITH THIS MPD IS RECORDED IN THE AIRCRAFT LOGBOOK Reference Publications: P & M Aviation Ltd Service Bulletin Number 141, Issue 3, dated 6 October 2016 Remarks: 1. Based on the required actions and compliance time, the CAA decided to issue this MPD with a request for comments, postponing the public consultation process until after publication. 2. Enquiries regarding this Mandatory Permit Directive should be referred to: GA Unit, Civil Aviation Authority, Safety and Airspace Regulation Group, Aviation House, Gatwick Airport South, West Sussex, RH6 0YR. Tel: +44 (0) ga@caa.co.uk 3. Enquiries regarding the Service Bulletin should be referred to: P & M Aviation Ltd, Elm Tree Park, Manton, Marlborough, Wiltshire. SN8 1PS. Tel: +44 (0) Mandatory Permit Directive Page 2 of 2

17 Civil Aviation Authority EMERGENCY MANDATORY PERMIT DIRECTIVE Number: E Issue date: 23 November 2016 In accordance with Article 41(1) of The Air Navigation Order 2016, as amended, the following action required by this Mandatory Permit Directive (MPD) is mandatory for applicable aircraft registered in the United Kingdom operating on a UK CAA Permit to Fly. Type Approval Holder s Name: P&M Aviation Ltd Type/Model Designation(s): Various, see below Title: Manufacturer: Applicability: Clevis Pin / Split Ring Installations Inspection / Replacement P&M Aviation Ltd All Microlights where P & M Aviation Ltd is the Type Approval Holder: TADS No. Aircraft Type TADS No. Aircraft Type BM2 Gemini Sprint BM43 Mainair Mercury BM3 Tri-Flyer Sprint BM44 Pegasus Quasar 2 TC BM4 Gemini Flash BM45 Cyclone AX3//503 BM5 Panther XL-S BM46 Pegasus Quantum 15 (Rotax 2-stroke engines) BM9 Pegasus XL-R BM47 Mainair Blade BM10 Pegasus Flash BM50 Pegasus Quantum BM17 Pegasus Flash 2 BM51 Mainair Blade 912 BM14 Gemini Flash 2 BM53 Cyclone AX2000 BM16 Scorcher BM54 Mainair Rapier BM17 Pegasus Flash 2 BM56 Pegasus Quantum 15-HKS BM23 Gemini Flash 2 Alpha BM60 Mainair Blade 912S BM25 Pegasus XL-Q BM65 Flight Design CT2K (rudder control) BM27 Chaser S BM66 Pegasus Quik BM28 Pegasus Photon BM70 Quik GT450 BM31 Chaser S 1000 BM72 Flight Design CTSW (rudder control) BM33 Chaser S 508 BM77 QuikR BM37 Chaser S 447 BM80 Quik GTR BM38 Pegasus Quasar BM81 PulsR BM42 Pegasus Quasar TC BM83 Flight Design CTSL (rudder control) Mandatory Permit Directive Page 1 of 2

18 Civil Aviation Authority Mandatory Permit Directive SARG Reason: Following maintenance, a clevis pin came out of the RP-4 roll trim system pulley on a QuikR causing a left turn. The split ring securing the clevis pin had come out. It is not known if the ring was disturbed during the maintenance. The split ring which came out was the same spiral start pattern as that which has caused trouble before (see Service Bulletin 139). This pattern of ring has no positive stop, so that simple rotation of the ring (e.g. caused by it getting caught on something) will cause it to disengage. Disengagement of the split ring and subsequent clevis pin departure could affect the control of the aircraft. Effective Date: 24 November 2016 Compliance/Action: Compliance is required as follows, unless previously accomplished: 1. Before further flight, from the effective date of this MPD, inspect all clevis pin / split ring installations on the aircraft in accordance with paragraph 2 of P & M Aviation Ltd Service Bulletin If the inspection in paragraph 1 reveals any spiral start pattern split rings they must be replaced in accordance with paragraph 2 of P & M Aviation Ltd Service Bulletin 144 before further flight. 3. Record the inspection from paragraph 1 and any necessary rectification action from paragraph 2 in the aircraft technical log in accordance with paragraph 3 of P & M Aviation Ltd Service Bulletin Repeat the actions in paragraphs 1, 2 and 3 at each Permit to Fly revalidation. ENSURE COMPLIANCE WITH THIS MPD IS RECORDED IN THE AIRCRAFT LOGBOOK Reference Publications: Remarks: P & M Aviation Ltd Service Bulletin Number 144, Issue 3, dated 27 October This MPD was not posted for consultation because of the urgency of the requirement. 2. Enquiries regarding this Mandatory Permit Directive should be referred to: GA Unit, Civil Aviation Authority, Safety and Airspace Regulation Group, Aviation House, Gatwick Airport South, West Sussex, RH6 0YR. Tel: +44 (0) ga@caa.co.uk Mandatory Permit Directive Page 2 of 2

19 Civil Aviation Authority EMERGENCY MANDATORY PERMIT DIRECTIVE Number: E Issue date: 21 February 2017 In accordance with Article 41(1) of The Air Navigation Order 2016, as amended, the following action required by this Mandatory Permit Directive (MPD) is mandatory for applicable aircraft registered in the United Kingdom operating on a UK CAA Permit to Fly. Type Approval Holder s Name: P&M Aviation Ltd Title: Type/Model Designation(s): Various, see below Hang Bolt plus Lanyard Inspection / Replacement Manufacturer: Applicability: P&M Aviation Ltd All Microlights of the following types where P & M Aviation Ltd are the Type Approval Holder: TADS No. Aircraft Type Reason: BM44 Pegasus Quasar 2 TC BM46 Pegasus Quantum 15 (Rotax 2-stroke engines) BM50 Pegasus Quantum BM56 Pegasus Quantum 15-HKS BM66 Pegasus Quik BM70 Quik GT450 BM77 QuikR BM80 Quik GTR BM81 PulsR The lanyard on a hang bolt plus lanyard component was found to be under swaged which allowed it to detach at a low load. The lanyard is essential to stop the hang bolt pinch nut from slackening off. Should the pinch nut fall off there would not be anything to prevent the hang bolt from potentially migrating out of its housing and the wing would then detach. Effective Date: 21 February 2017 This problem was identified as a manufacturing deficiency of part number YQB and affected three batches of the component: A9835, A9868 and A9880. Mandatory Permit Directive E Page 1 of 2

20 Civil Aviation Authority Mandatory Permit Directive Safety and Airspace Regulation Group Compliance/Action: Compliance is required as follows, unless previously accomplished: 1. Before further flight, inspect the hang bolt plus lanyard, part number YQB If the lanyard is from batch number A9835, A9868 or A9880, before further flight, remove the hang bolt plus lanyard from the aircraft and return to P & M Aviation Ltd for replacement. Note: The hang bolt plus lanyard part number and batch number are marked on the sleeve shrunk on to the lanyard. 2. Record the inspection from paragraph 1 and any necessary rectification action in the aircraft technical log in accordance with paragraph 3 of P & M Aviation Ltd Service Bulletin Repeat the actions in paragraphs 1 and 2 at each Permit to Fly revalidation. ENSURE COMPLIANCE WITH THIS MPD IS RECORDED IN THE AIRCRAFT LOGBOOK Reference Publications: Remarks: P & M Aviation Ltd Service Bulletin Number 146 Issue 1 dated 6 January This MPD was not posted for consultation because of the urgency of the requirement. 2. Enquiries regarding this Mandatory Permit Directive should be referred to: GA Unit, Civil Aviation Authority, Safety and Airspace Regulation Group, Aviation House, Gatwick Airport South, West Sussex, RH6 0YR. Tel: +44 (0) ga@caa.co.uk Mandatory Permit Directive E Page 2 of 2

21 Civil Aviation Authority EMERGENCY MANDATORY PERMIT DIRECTIVE Number: E Issue date: 15 May 2017 In accordance with Article 41(1) of The Air Navigation Order 2016, as amended, the following action required by this Mandatory Permit Directive (MPD) is mandatory for applicable aircraft registered in the United Kingdom operating on a UK CAA Permit to Fly. Type Approval Holder s Name: P&M Aviation Ltd Type/Model Designation(s): Various, see below Title: Rigging Cables with Roll Swaged End Terminals Inspection / Replacement Manufacturer: Applicability: P&M Aviation Ltd All Microlights of the following types where P & M Aviation Ltd are the Type Approval Holder: TADS No. Aircraft Type BM4 BM10 BM14 BM16 BM17 BM23 BM43 BM47 Gemini Flash Pegasus Flash Gemini Flash 2 Scorcher Pegasus Flash 2 Gemini Flash 2 Alpha Mainair Mercury Mainair Blade BM51 Mainair Blade 912 BM54 Mainair Rapier BM60 Mainair Blade 912S BM70 Quik GT450 BM77 QuikR BM80 Quik GTR BM81 PulsR Mandatory Permit Directive E Page 1 of 3

22 Civil Aviation Authority Mandatory Permit Directive Safety and Airspace Regulation Group Reason: A P&M Quik GT450 in a flying school had a partial failure of a lower side rigging cable (Part No. YQD-045) when recovering from a spiral manoeuvre, within the limits of the flight envelope. These cables are arranged in pairs, to give a backup load path. The second cable carried the load and the aircraft landed safely. This is the only recorded lower side cable failure since The partial failure was at the edge of the roll swaged terminal end. The alternative cable terminations using Nicopress sleeves and thimbles allow more progressive flexing of the cable. The incident Quik GT450 lower side rigging cables had been in use for 1050 hours and 9 years. The aircraft had been subject to an accident and rebuilt once in its life. It was also operated quite near the coast where it is probable that sea air chlorides could have affected the material. There were corrosion pits in the S316 stainless steel material which accelerate fatigue failures. CLSCC (Chloride Stress Corrosion Cracking) is known to affect stainless steel. The cable fitting was at the bottom end of the cable, where solutions can wick down it and collect. The strand failures were caused by bending and tensile fatigue because of cracks propagating from scratches and corrosion pits on the surface. All the remaining cables had broken strands at the edge of the roll swaged terminals. Some of these strands had been failed for some time, as shown by discolouration of the failure surfaces. The cable is 7 cores of 7 strands construction. Failure of a lower rigging cable would potentially reduce the integrity of the wing and hazard the aircraft. Effective Date: 15 May 2017 Mandatory Permit Directive E Page 2 of 3

23 Civil Aviation Authority Mandatory Permit Directive Safety and Airspace Regulation Group Compliance/Action: Compliance is required as follows, unless previously accomplished: 1. Before further flight, for lower side, front and rear rigging cables with roll swaged terminal ends with more than 750 flying hours or 7 years of service, whichever comes first, visually inspect at the edge of the roll-swaged terminal(s) using a magnifying glass with a power of at least 3x. Inspect closely for damage i.e. broken strands, corrosion, mechanical damage or slippage. If any damage is found, replace the affected cable before further flight. If no damage is found, replace the cable within 25 flying hours. See paragraphs 1 and 2 of P & M Aviation Ltd Service Bulletin 147 including the warning in paragraph Within 25 flying hours, for lower side, front and rear rigging cables with roll swaged terminal ends with less than 750 flying hours and less than 7 years of service, visually inspect at the edge of the rollswaged terminal(s) using a magnifying glass with a power of at least 3x. Inspect closely for damage i.e. broken strands, corrosion, mechanical damage or slippage. If any damage is found, replace the affected cable before further flight. If no damage is found, replace the cable at 750 flying hours or 7 years of service, whichever comes first. See paragraphs 1 and 2 of P & M Aviation Ltd Service Bulletin 147 including the warning in paragraph Removal and replacement of any airframe structural cable requires a duplicate inspection - see paragraph 3 of P & M Aviation Ltd Service Bulletin Record the inspection from paragraph 1 or paragraph 2 and any necessary rectification action in the aircraft technical log in accordance with paragraph 3 of P & M Aviation Ltd Service Bulletin Repeat the inspection in paragraph 2 at each Permit to Fly revalidation and replace damaged cables as necessary. Replace the cables at 750 flying hours or 7 years of service, whichever comes first. ENSURE COMPLIANCE WITH THIS MPD IS RECORDED IN THE AIRCRAFT LOGBOOK Reference Publications: Remarks: P & M Aviation Ltd Service Bulletin Number 147 Issue 1 dated 10 May This MPD was not posted for consultation because of the urgency of the requirement. 2. Enquiries regarding this Mandatory Permit Directive should be referred to: GA Unit, Civil Aviation Authority, Safety and Airspace Regulation Group, Aviation House, Gatwick Airport South, West Sussex, RH6 0YR. Tel: +44 (0) ga@caa.co.uk Mandatory Permit Directive E Page 3 of 3